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The Calculation of the Three-Dimensional Turbulent Boundary Layer: Part III. Comparison of Attachment-Line Calculations with Experiment

Published online by Cambridge University Press:  07 June 2016

N. A. Cumpsty  and
M. R. Head
N. A. Cumpsty
Affiliation:
Cambridge University Engineering Department
M. R. Head
Affiliation:
Cambridge University Engineering Department
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Summary

Wind tunnel measurements have been made of the attachment-line boundary layer on a swept wing. The combination of a 4-5 in (114 mm) nose radius and 60° angle of sweep enabled a wide range of values of the parameter V2/(v dU/dx) (denoted here by C*), to be covered, and gave a thick enough boundary layer for the velocity profiles to be accurately measured. Pitot traverses were performed for values of C* from 0·59 × 105 to 3·7 × 105. Without a trip wire fitted the attachment-line flow was laminar over the full range and the measured velocity profiles agreed closely with the theory for an infinite swept wing. With a large trip wire fitted, a transition régime was observed in the range 0·6 × 105 < C* < 1·4 × 105, and at higher values of C* the flow was fully turbulent and showed good agreement with the earlier calculations of Cumpsty and Head. Preston tubes were used for skin friction measurements in fully turbulent conditions and a hot wire was used to explore the development of turbulence in the transition régime.

Type
Research Article
Information
Aeronautical Quarterly , Volume 20 , Issue 2 , May 1969 , pp. 99 - 113
Copyright
Copyright © Royal Aeronautical Society. 1969

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References

1. Cumpsty, N. A. and Head, M. R. The calculation of three-dimensional turbulent boundary layers. Part II: Attachment-line flow on an infinite swept wing. Aeronautical Quarterly, Vol, XVIII, p. 150, May 1967.CrossRefGoogle Scholar
2. Gaster, M. On the flow along swept leading edges. Aeronautical Quarterly, Vol. XVIII, p. 165, May 1967. (Also College of Aeronautics, Note Aero 167, 1965.)CrossRefGoogle Scholar
3. Pfenninger, W. Flow phenomena at the leading edge of a swept wing. AGARDograph 97, Recent development in boundary-layer research, Part IV, 1965.Google Scholar
4. Gregory, N. and Love, E. M. Laminar flow on a swept leading edge: final progress report. NPL Aero. Memo. 26; ARC 27 979 (unpublished), 1965.Google Scholar
5. Rosenhead, L. (Editor). Laminar boundary layers. Oxford University Press, 1963.Google Scholar
6. Preston, J. H. The determination of turbulent skin friction by means of pitot tubes. Journal of the Royal Aeronautical Society, Vol. 58, p. 109, 1954.CrossRefGoogle Scholar
7. Patel, V. C. Calibration of the Preston tube and limitations on its use in pressure gradients. Journal of Fluid Mechanics, Vol. 23, Part 1, p. 185, 1965.CrossRefGoogle Scholar
8. Gregory, N. Laminar flow on a swept leading edge: second progress report. NPL Aero Memo. 12; ARC 25 814 (unpublished), 1964.Google Scholar
9. Preston, J. H. The minimum Reynolds number for a turbulent boundary layer and the selection of a transition device. Journal of Fluid Mechanics, Vol. 3, Part 4, p. 373, 1957.CrossRefGoogle Scholar
10. Schubauer, G. B. and Klebanoff, P. S. Contributions on the mechanism of boundary-layer transition. Proceedings of the Symposium on Boundary-Layer Effects in Aerodynamics, National Physical Laboratory, 1955.Google Scholar
11. Head, M. R. Entrainment in the turbulent boundary layer. ARC R& M 3152,1958.Google Scholar
12. Mager, A. Generalisation of boundary-layer momentum integral equations to three-dimensional flows, including those of rotating systems. NACA Report 1067, 1952.Google Scholar
13. Johnston, J. P. On the three-dimensional turbulent boundary layer generated by secondary flow. Journal of Basic Engineering, American Society of Mechanical Engineers, Series D, Vol. 82, p. 233,1960.CrossRefGoogle Scholar